Aerial vessel



April 10, 1928.

O. L. DALLY AERIAL VESSEL Filed Oct. 22, 1925 '3 Sheets-Sheet lINVENTOR. 0021a" lflfl lg,

r ATTORNEY.

April 10, 1928.

0. L. DALLY AERIAL VESSEL 3 Sheets-Sheet 2 Filed Oct. 22, 1925 INVENTOR.

April- 10, 1928.

O. L. DALLY AERIAL VESSEL Filed Oct. 22, 1925 5 Sheets-5heet 3 INVENTOR.

A TTORNEY.

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Patented Apr. 10, 1928.

UNITED STATES OVID I. DAILY, 0F CLEVELAND, OHIO.

AERIAL VESSEL.

Application filed October 22, 1925. Serial No. 64,175.

This invention relates to aerial vessels, such as the aeroplane orsea-plane type, and has for its object to provide, in a manner ashereinafter set forth, a vessel of such class, whereby the resultantforce from a Magnus effect is utilized vertically at right angles to thedirection of the wind and in the direction towards which the surface ofthe object is moving at the point of contact with the an for materiallyincreasing the lifting power of the vessel over known constructions whentravelling at the same rate of speed, and further to overcome anydifliculty in taking off and landing.

A furtherobject of the invention is to provide, in a manner ashereinafter set forth, a vessel of the class referred to, having themain supporting surfaces thereof in the form of a pair of oppositelyextending air driven rotors to produce a Magnus effect and with thevessel creating its own air speed for the rotors without depending onthe speed or direction of the Wind and with the rotors disposedwherebythe resulting force from the Magnus effect would always be vertical solong as the vessel is flying horizontally and and so that the resultantlift would be determined in part'by the speed at which the rotors arerevolved, or whereby the resultant force from the Magnus effect will bedisposed at right'angles to the direction of travel of the vessel.

Further objects of the invention are to provide in a manner ashereinafter set forth, a vessel of the class referred to, which iscomparatively simple in its construction and arrangement, strong,durable, readily assembled, thoroughly eficient in its use, andcomparatively inexpensive With the foregoing and other objects in view,the invention consists of the novel construction, combination andarrangements of parts, as hereinafter more specifically described andillustrated in the accompanying drawings, wherein is shown an embodimentof the invention, but it is to be understood that changes, variationsand modifications can be resorted to which come within the scope of theclaims hereunto appended.

in the drawings wherein like reference characters denote correspondingparts throughout the several views Figure l is a top plan view of anaerial vessel of the aeroplane type, in accordance 1 with thisinvention.

, wards the inner end of a sustaining element.

Figure 6 is a fragmentary view, in sectional plan, illustrating theinner terminal portion of a sustaining element.

Figure 7 is a section on line 7-7, Figure 3.

Figure 8 is a section on line 8-8, Figure 5. 1

Figure 9 is a perspective view of the shield for a turbine.

Figures 10 and 11 are diagrammatical views illustrating the resultingforces with respect to the revoluble sustaining elements.

Referring to the drawings in detail, 1 and 2 generally indicate therevoluble sustaining elements each in the form of a rotor and oneextending in an opposite direction with respect to the other. The rotorsare horizontally disposed and each extends at right angles with respectto the body of the plane. Connected to the inner end of each of thesustaining elements is a wind driven turbine referred to generally bythe reference character 3. The propeller of the plane is indirated at 4,the ailerons or side stabilizers and controls are indicated at 5, 6, thefuselage at 7, the horizontal. stabilizers at 8, 9, and the elevators at10, 11.

Each revolublc sustaining element consists of a series of circularsupports referred to generally by the reference character 12 andconsisting of a hub 13, having projecting therefrom a series of radiallydisposed arms or spokes 14, connected at their outer ends to a rim 15.lhe body portion 16 of each of the sustaining elements is formed fromplane cloth and is secured to and maintained in cylindrical form by thesupports 12. Gonnected to the outer end of each sustaining element is ameans for confining. the air current thereon, that is to say to preventthe current from spreading off the outer end of the sustaining element.The said means consists of an endless tip 17 projecting a substantialdistance in a lateral direction from and with respect to the peripheryof the sustaining element. The tip T formed from a circular of l int"lid

ametenthan the diameter of the body portion 16, positionedagainst,arranged concentrically with respect to and closin the outer endof the sustaining element. ecured to the inner end of each sustainingelement is the wind driven turbine 3 therefor, and said turbine as wellas the sustaining element is fixed to a tapered shaft 18, which isjournaled at its inner end in the fuselage 7 The blades of each of theturbines are indicated at 19 and associated therewith is a depend ingcurved shield 20, which is supported by the brackets 21, secured to andprojecting laterally from the fuselage 7 Connected to the upper end ofthe shield 20 by a support ing bracket 22 is afunnel-shaped air director23 for directing the air to the blade of the turbine. See Figure 5.

The funnels project forwardly from the turbines 3 and take the air fromthe propeller 4 and direct it against the blades of the turbine for thepurpose of revolving the sustainin elements 1, 2.

The e ect obtained by the revolving sustaining elements is the Magnuseffect and owing to the horizontal disposition of the sustainingelements the resultantforce from the Magnus effect will extend at rightangles to the direction of travel of the plane.

To more clearly define the resultant force obtained by the horizontallydisposed re-. voluble sustaining elements, attentlon is directed toFigures 10 and .11, and with reference thereto A indicates thecylindrical or round revoluble sustaining element. When the element isnot revolving there will be a positive pressure at point N and anegative pressure at point T. Pressures at P and V are necessarily.equal as shown in Figure 10. When the element is revolving as in Figure11, there will be a less or negative intensity at point V and a reateror positive intensity created at point This is due to the viscosity ofthe air. At any rate it is the result of the "action of air upon anyrevolvin object as was first noticed by Ma nus. he resultin force R isalways vertical directly at rig t angles to the direction of the windand in the direction towards which the surface of the element is movingat the point of contactwith the air as the elements are horizontallydisposed and not vertically arranged.

The sustaining elements of the plane, in accordance with thisinvention,do-m)t depend upon a wind for the operation thereof as the plane alwayscreates its own air speed or its own airto provide for the operation ofthe revolving sustaining elements without in any manner dependinguponthe speed or direction of a wind. As the sustaining elements aredisposed horizontally, the resulting force is always verticalas long asthe plane is flying horizontal and the resulting lift is determined inpart by the speed at mamas which the sustaining elements are revolved.With the sustaining elements placed horizontally and with the bottomside revolving into the wind, the resulting force will be vertical andmany times greater, especially at speeds below twenty-five miles an hourthan can be obtained by any present type of wing or sustaining element,under such conditions materially increasing the lifting power of theplane, over known constructions, when travelling at the same rate ofspeed, and further overcoming any difficulty when taking off or landing.

'Although the body portion of each of the sustaining elements has beenreferred to as constructed of ordinary aeroplane cloth material, saidbody portion can be set up of light metallic sheeting, such as is nowused in metal aeroplanes. The surface of the body portion of thesustaining element may be rough or smooth, there being no practicaldifference in the result obtained in either.

What I claim is z- 1. An aerial vessel comprising a pair of lengthwisealigned revoluble cylindrical sustaining elements to obtain a Magnuseffect with the resulting force extending at right angles to thedirection of travel of the vessel, and an air driven turbine fixed tothe inner end of each of said elements, bodily revolving therewith andhaving the operating air therefor directed from the propeller of thevessel on the operation thereof.

2. An aerial vessel com rising a pair of lengthwise aligned revoliiblecylindrical sustaining elements to obtain a Magnus effeet with theresulting force extending at right angles to the direction of travel ofthe vessel and each having its entire outer curved. periphersimultaneously exposed during the revo ving thereof, and an air driventurbine fixed to the inner'end of each of said elements, bodilyrevolving therewith and having the operating air therefor directed .fromthe pro eller of the vessel on the operation thereof? 3. An aerialvessel com rising a pair of lengthwise aligned revo uble c lindricalsustaining elements to obtain a agnus effeet with the resulting forceextendin at right angles to the direction of travel 0 the vessel andeach having its entire outer curved periphery simultaneously exposedduring the revolving thereof, means at the outer end of each of saidelements to provide a tip therefor corresponding in contour to the shapethereof, and an' air driven turbine fixed to the inner end of each ofsaid elements, bodily revolving therewith and having the operating airtherefor directed from the propeller of the vessel on the operationthereof.

4. An aerial vessel comprising horizontally disposed, revoluble,cylindrical air driven sustaining elements for utilizing the mamasresulting force from the Ma nus effect in a direction at rightangles tothe travel of the vessel and driven at their inner ends from airdirected from the propeller of the vessel during its operation, each ofsaid elements including at its inner end an air driven turbine bodilyrevoluble therewith.

5. An aerial vessel comprising horizontally disposed, revoluble,cylindrical air driven sustaining elements for utilizing the resultingforce from the Magnuseifect in a direction at right angles to the travelof the Vessel and driven at their inner ends from air directed from thepropeller of the vessel during its operation, each of said elementsincluding at its inner end an air driven turbine bodily rcvolubletherewith, and an air directing means associated with each of saidturbines for receiving the air directed from the propeller.

.6. In an aerial vessel, a fuselage, a propeller at the forward endthereof, a pair of oppositely extending revoluble, cylindricalsustaining elements, each supported from one side of the fuselage anddisposed at right angles with respect thereto and obtaining a Magnuseifect with the resulting force extending at right angles to thedirection of travel of the essel and each having its entire outer curvedperiphery simultaneously exposed during the revolving thereof, and anair driven turbine fixed to the inner end of each of said elements,bodily revolving therewith and having the operating air therefordirected from said propeller on the operation thereof.

7. In an aerial vessel, a fuselage, a pro peller at the forward endthereof, a pair of oppositely extending revoluble, cylindricalsustaining elements, each supported from one side of the fuselage anddisposed at right angles with respect thereto and obtaining a Magnuseffect with theresulting force extending at right angles to thedirection of travel of the vessel and each having its en-- tire outercurved periphery simultaneously exposed during the revolving thereof, anair driven turbine fixed to the inner end of each of said elements,bodily revolving therewith and having the operating air therefordirected from said propeller on the operation thereof, and an airdirecting means associated with each of said turbines and receiving theair directed from the propeller.

In testimony whereof, I afiix my signature hereto.

OVID L. DALLY.

